[Federal Register Volume 59, Number 22 (Wednesday, February 2, 1994)]
[Unknown Section]
[Page 0]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 94-452]


[[Page Unknown]]

[Federal Register: February 2, 1994]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 93-NM-120-AD; Amendment 39-8794; AD 94-01-12]

 

Airworthiness Directives; Airbus Industrie Model A310-200 and 
A310-300 Series Airplanes

AGENCY: Federal Aviation Administration, DOT.

ACTION: Final rule.

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SUMMARY: This amendment supersedes an existing airworthiness directive 
(AD), applicable to all Airbus Industrie Model A310-200 and A310-300 
series airplanes, that currently requires inspections and test to 
detect broken or missing vespel bushes in the flap universal joint 
assemblies, and replacement of universal joint bushes, if necessary. 
This amendment adds a terminating modification for the currently 
required inspections and tests. This amendment is prompted by the 
development of a modification that will improve the integrity of the 
flap universal joints. The actions specified by this AD are intended to 
prevent rupture of the flap universal joints, subsequent partial loss 
of lift in one wing, and reduced controllability of the airplane.

DATES: Effective March 4, 1994.
    The incorporation by reference of Airbus Industrie Service Bulletin 
A310-27-2059, dated March 1, 1993, as listed in the regulations, is 
approved by the Director of the Federal Register as of March 4, 1994.
    The incorporation by reference of Airbus Industrie Service Bulletin 
A310-27-2054, Revisions 2, dated November 9, 1990, as listed in the 
regulations, was approved previously by the Director of the Federal 
Register as of September 11, 1991 (56 FR 37462, August 7, 1991).

ADDRESSES: The service information referenced in this AD may be 
obtained from Airbus Industrie, 1 Rond Point Maurice Bellonte, 31707 
Blagnac Cedex, France. This information may be examined at the Federal 
Aviation Administration (FAA), Transport Airplane Directorate, Rules 
Docket, 1601 Lind Avenue SW., Renton, Washington; or at the Office of 
the Federal Register, 800 North Capitol Street NW., suite 700, 
Washington, DC.

FOR FURTHER INFORMATION CONTACT:
Stephen Slotte, Aerospace Engineer, Standardization Branch, ANM-113, 
FAA, Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, 
Washington 98055-4056; telephone (206) 227-2797; fax (206) 227-1320.

SUPPLEMENTARY INFORMATION: A proposal to amend part 39 of the Federal 
Aviation Regulations by superseding AD 91-16-05, Amendment 39-7095 (56 
FR 37462, August 7, 1991), which is applicable to all Airbus Industrie 
Model A310-200 and A310-300 series airplanes, was published in the 
Federal Register on October 6, 1993 (58 FR 52041). The action proposed 
to add a requirement to modify the flap universal joint assemblies. 
Installation of this modification would terminate the currently 
required inspections and tests to detect broken or missing vespel 
bushes in the flap universal joint assemblies.
    Interested persons have been afforded an opportunity to participate 
in the making of this amendment. Due consideration has been given to 
the two comments received.
    Both commenters support the proposal.
    After careful review of the available data, including the comments 
noted above the FAA has determined that air safety and the public 
interest require the adoption of the rule as proposed.
    The FAA estimates that 25 airplanes of U.S. registry will be 
affected by this AD.
    The inspections and tests currently required by AD 91-16-05 take 
approximately 5 work hours to accomplish, at an average labor cost of 
$55 per work hour. Based on these figures, the total cost impact on 
U.S. operators of the actions previously required by AD 91-16-05 is 
estimated to be $6,875, or $275 per airplane, per inspection and 
testing cycle.
    It will take approximately 47 work hours per airplane to accomplish 
the modification required by this new AD action, at an average labor 
rate of $55 per work hour. Required parts will cost approximately 
$1,000 per airplane. Based on these figures, the total additional cost 
impact associated with the modification requirements of this AD on U.S. 
operators is estimated to be $89,625, or $3,585 per airplane.
    The cost figures discussed above are based on assumptions that no 
operator has yet accomplished the requirements of this AD action.
    The regulations adopted herein will not have substantial direct 
effects on the States, on the relationship between the national 
government and the States, or on the distribution of power and 
responsibilities among the various levels of government. Therefore, in 
accordance with Executive Order 12612, it is determined that this final 
rule does not have sufficient federalism implications to warrant the 
preparation of a Federalism Assessment.
    For the reasons discussed above, I certify that this action (1) is 
not a ``significant regulatory action'' under Executive Order 12866; 
(2) is not a ``significant rule'' under DOT Regulatory Policies and 
Procedures (44 FR 11034, February 26, 1979); and (3) will not have a 
significant economic impact, positive or negative, on a substantial 
number of small entities under the criteria of the Regulatory 
Flexibility Act. A final evaluation has been prepared for this action 
and it is contained in the rules Docket. A copy of it may be obtained 
from the Rules Docket at the location provided under the caption 
ADDRESSES.

List of Subjects in 14 CFR Part 39

    Air transportation, Aircraft, Aviation safety, Incorporation by 
reference, Safety.

Adoption of the Amendment

    Accordingly, pursuant to the authority delegated to me by the 
Administrator, the Federal Aviation Administration amends 14 CFR part 
39 of the Federal Aviation Regulations as follows:

PART 39--AIRWORTHINESS DIRECTIVES

    1. The authority citation for part 39 continues to read as follows:

    Authority: 49 U.S.C. App. 1354(a), 1421 and 1423; 49 U.S.C. 
106(g); and 14 CFR 11.89.


Sec. 39.13  [Amended]

    2. Section 39.13 is amended by removing amendment 39-7095 (56 FR 
37462, August 7, 1991), and by adding a new airworthiness directive 
(AD), amendment 39-8794, to read as follows:

94-01-12 Airbus Industrie: Amendment 39-8794. Docket 93-NM-120-AD. 
Supersedes AD 91-17-05, Amendment 39-7095.

    Applicability: All Model A310-200 and A310-300 series airplanes, 
certificated in any category.
    Compliance: Required as indicated, unless accomplished 
previously.
    To prevent rupture of the flap universal joints, subsequent 
partial loss of lift in one wing, and reduced controllability of the 
airplane, accomplish the following:
    (a) Prior to the accumulation of 5,500 total landings, or within 
350 hours time-in-service after September 11, 1991 (the effective 
date of AD 91-16-05, Amendment 39-7095), whichever occurs later, and 
thereafter at intervals not to exceed 3,500 landings, perform 
repetitive visual inspections and electrical continuity tests of the 
flap system.
    (b) If any universal joint bushes are missing or broken, prior 
to further flight, replace the bushes with new bushes in accordance 
with Airbus Industrie Service Bulletin A310-27-2054, Revision 2, 
dated November 9, 1990. After replacement, repeat the inspections 
required by paragraph (a) of this AD at intervals not to exceed 
3,500 landings.
    (c) Within 3,500 landings after the effective date of this AD, 
modify the flap universal joint assemblies (Airbus Industrie 
Modification 10091D20285) in accordance with Airbus Industrie 
Service Bulletin A310-27-2059, dated March 1, 1993. Accomplishment 
of this modification constitutes terminating action for the 
inspection and test requirements of this AD.
    (d) Modification of the flap universal joint assemblies (Airbus 
Industrie Modification 10091D20285) in accordance with Airbus 
Industrie Service Bulletin A310-27-2059, dated March 1, 1993, 
constitutes terminating action for the inspection and test 
requirements of this AD.
    (e) An alternative method of compliance or adjustment of the 
compliance time that provides an acceptable level of safety may be 
used if approved by the Manager, Standardization Branch, ANM-113, 
FAA, Transport Airplane Directorate. Operators shall submit their 
requests through an appropriate FAA Principal Maintenance Inspector, 
who may add comments and then send it to the Manager, 
Standardization Branch, ANM-113.

    Note: Information concerning the existence of approved 
alternative methods of compliance with this AD, if any, may be 
obtained from the Standardization Branch, ANM-113.

    (f) Special flight permits may be issued in accordance with FAR 
21.197 and 21.199 to operate the airplane to a location where the 
requirements of this AD can be accomplished.
    (g) The inspections, testing, and replacement shall be done in 
accordance with Airbus Industrie Service Bulletin A310-27-2054, 
Revision 2, dated November 9, 1990. The incorporation by reference 
of this document was approved previously by the Director of the 
Federal Register, in accordance with 5 U.S.C. 552(a) and 1 CFR part 
51, as of September 11, 1991 (56 FR 37462, August 7, 1991). The 
modification shall be done in accordance with Airbus Industrie 
Service Bulletin A310-27-2059, dated March 1, 1993. The 
incorporation by reference of this document is approved by the 
Director of the Federal Register, in accordance with 5 U.S.C. 552(a) 
and 1 CFR part 51. Copies of these documents may be obtained from 
Airbus Industrie, 1 Rond Point Maurice Bellonte, 31707 Blagnac 
Cedex, France. Copies may be inspected at the FAA, Transport 
Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington; or 
at the Office of the Federal Register, 800 North Capitol Street, 
NW., suite 700, Washington, DC.
    (h) This amendment becomes effective on March 4, 1994.

    Issued in Renton, Washington, on January 4, 1994.
Darrell M. Pederson,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 94-452 Filed 2-1-94; 8:45 am]
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